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Viewing 1 to 30 of 244
2017-11-20
WIP Standard
J3014
This SAE Recommended Practice provides test procedures, requirements, and equipment recommendations for the methods of the measurement that characterizes potential design failures by utilizing a step stress approach to subject a device under test to thermal, vibration, and electrical stresses of types and levels beyond what it may see in actual use, but which will rapidly induce failure modes, allowing them to be detected and corrected.
CURRENT
2017-11-20
Standard
J587_201711
This SAE Standard provides test procedures, requirements, and guidelines for vehicular license plate illumination devices.
2017-11-18
WIP Standard
AIR26B
This SAE Aerospace Information Report (AIR) records the dimensions for the No. 70-90, 70L-90, 80-100 and 80L-100 dual rotation propeller shaft ends, which have been deleted from ARP375.
CURRENT
2017-11-16
Standard
J3003_201711
This SAE Recommended Practice provides dimensional specifications for the 41/2 and 53/4 inch general service sealed lighting units, intended for use in such applications as motorcycle headlamps, military headlamps, industrial machinery headlamps, fog lamps, spot lamps, etc. See Figures 1 and 2 and Tables 1 and 2.
CURRENT
2017-11-15
Standard
AMS4951J
This specification covers one grade of commercially pure titanium in the form of wire for welding filler metal.
CURRENT
2017-11-09
Standard
ARP991C
This document recommends design objectives for navigation, position, and anticollisionlight systems for visual detection and collision avoidance between airplanes in flight and on the ground. Customers for new airplanes or lighting components, and designers or manufacturers may take advantage of this document in specifying the initial requirements that, in most cases, significantly exceed the applicable minimum intensities as shown in the Federal Aviation Regulations as well provide better stability, longer life and lower operating costs.
2017-10-30
Article
The NuEntry e-latch is a prelude to vehicle side doors that automatically open and close on command.
2017-10-26
WIP Standard
ARP6812
This SAE Aerospace Recommended Practice (ARP) covers the functional, design, construction, and test requirements for Brake Temperature Monitoring Systems (BTMS), and sometimes referred to as Brake Temperature Indication Systems (BTIS). The BTMS is limited to aircraft where a dispatch indication and brake temperature indication is required. The scope of this BTMS equipment shall be limited to the 1) brake temperature sensor or indicator, 2) temperature reference measurement, if required, and 3) processing and communication of brake temperature. This recommended practice will not address cockpit ergonomics and aircraft operating procedures.
2017-10-16
WIP Standard
J2838
This SAE standard provides test procedures, performance requirements, design guidelines and installation guidelines for full adaptive forward lighting systems (AFS).
2017-10-13
Technical Paper
2017-01-5018
Subhash Hanmant Bhosale, Manohar Goud Kalal, Ashish Kumar Sahu
Abstract In today’s cost-competitive automotive market, use of finite element simulations and optimization tools has become crucial to deliver durable and reliable products. Simulation driven design is the key to reduce number of physical prototypes, design iterations, cost and time to market. However, simulation driven design optimization tools have struggled to find global acceptance and are typically underutilized in many applications; especially in situations where the algorithms have to compete with existing know-how decision making processes. In this study, systematic multi-phase approach for optimization driven design is presented. Approach includes three optimization phases. In first phase, topology optimization is performed on concept BIW design volume to identify critical load paths. Architectural inputs from topology are used to design base CAD.
CURRENT
2017-10-10
Standard
J95_201710
This SAE Standard provides performance and general design requirements and related test procedures for headlamps for use on industrial wheeled equipment that may be operated on public roads.
2017-10-08
Technical Paper
2017-01-2425
Ramit Verma, Ramdas R Ugale
Abstract On two wheelers, magneto/alternator generates either single/three phase AC power and Regulator Rectifier Unit (RRU) does regulated rectification to charge the battery. In order to face the requirements of 2-wheeler engine with respect to upcoming stringent regulations like electronic fuel injection (EFI), anti-lock braking system (ABS), automatic headlamp on (AHO) in emerging markets like India; vehicles demand more electrical power from batteries. This demands higher power from alternator and consequently from RRU. Requirement of higher output power presents challenges on regulator rectifier unit in terms of size, power dissipation management and reliability. In this paper, improved performance of MOSFET based RRU is discussed in comparison to Silicon Controlled Rectifier (SCR) based RRU. The motivation/benefits of MOSFET based design is described along with the thermal behavior and temperature coefficient performance of RRU with test results.
2017-10-04
Article
GKN Driveline’s VL3 constant velocity joint system is a lighter, more efficient and stronger CV joint that delivers increased torque in a more compact design.
2017-09-21
Article
WABCO Holdings signed a long-term cooperation agreement in late August with Nexteer Automotive to collaborate on the development and supply of active steering systems for medium- and heavy-duty commercial vehicles using Nexteer's advanced steering assistance technology.
2017-09-21
WIP Standard
AIR8012
The purpose of the document is to provide the guidelines of the technological approach for developing a PHM system for EMAs with particular reference to their possible use as primary flight control actuators. It provides a basic description of the physics of the most common degradation processes,a reliability assessment and a discussion on the signals, with the associated data processing, required to build up an effective health monitoring system.
2017-09-19
Technical Paper
2017-01-2028
Steven Nolan, Patrick Norman, Graeme Burt, Catherine Jones
Abstract Turbo-electric distributed propulsion (TeDP) for aircraft allows for the complete redesign of the airframe so that greater overall fuel burn and emissions benefits can be achieved. Whilst conventional electrical power systems may be used for smaller aircraft, large aircraft (~300 pax) are likely to require the use of superconducting electrical power systems to enable the required whole system power density and efficiency levels to be achieved. The TeDP concept requires an effective electrical fault management and protection system. However, the fault response of a superconducting TeDP power system and its components has not been well studied to date, limiting the effective capture of associated protection requirements. For example, with superconducting systems it is possible that a hotspot is formed on one of the components, such as a cable. This can result in one subsection, rather than all, of a cable quenching.
2017-09-19
Technical Paper
2017-01-2059
Enrico Cestino, Giacomo Frulla, Renzo Duella, Paolo Piana, Francesco Pennella, Francesco Danzi
Abstract Future generations of civil aircrafts and unconventional unmanned configurations demand for innovative structural concepts to improve the structural performance, and thus reduce the structural weight, but also to allow possible material couplings to be made. Static and dynamic aeroelastic stability can be altered by these couplings. It is therefore necessary to use an accurate and computationally efficient beam model during the preliminary design phase. A stiffened box, made of isotropic material, but with the stiffeners oriented so that they originate the expected bending/torsion coupling, is considered in the present work. The overall equivalent bending, torsional and coupled stiffness is derived by means of homogenization of the shell skin and of the stiffener plate stiffness. A new equivalent homogeneous orthotropic material is determined and introduced into the equivalent plate configuration.
2017-09-19
Technical Paper
2017-01-2061
Andrea Cravana, Gerardo Manfreda, Enrico Cestino, Giacomo Frulla, Robert Carrese, Piergiovanni Marzocca
Abstract An accurate aeroelastic assessment of powered HALE aircraft is of paramount importance considering that their behaviour contrasts the one of conventional aircraft mainly due to the use of high aspect-ratio wings with distributed propulsion systems. This particular configuration shows strong dependency of the wing natural frequencies to the propulsion distribution and operating conditions. Numerical and experimental investigations are carried out to better understand the behaviour of flexible wings, focusing on the effect of distributed electric propulsion systems. Several configurations are investigated, including a single propulsion system using an engine pod (a weight with embedded electric motor, a propeller, and the wing-attached structure) installed at selected spanwise positions, and configurations with two and three propellers.
2017-09-19
Technical Paper
2017-01-2058
Francesco Noziglia, Paolo Rigato, Enrico Cestino, Giacomo Frulla, Alfredo Arias-Montano
Abstract Innovative aircraft design studies have noted that uncertainty effects could become significant and greatly emphasized during the conceptual design phases due to the scarcity of information about the new aero-structure being designed. The introduction of these effects in design methodologies are strongly recommended in order to perform a consistent evaluation of structural integrity. The benefit to run a Robust Optimization is the opportunity to take into account uncertainties inside the optimization process obtaining a set of robust solutions. A major drawback of performing Robust Multi-Objective Optimization is the computational time required. The proposed research focus on the reduction of the computational time using mathematic and computational techniques. In the paper, a generalized approach to operate a Robust Multi-Objective Optimization (RMOO) for Aerospace structure using MSC software Patran/Nastran to evaluate the Objectives Function, is proposed.
2017-09-19
Technical Paper
2017-01-2074
Thorsten Dillhoefer, Fatih Erdinc
Ever increasing process applications inspire us, as suppliers of aircraft, structural-assembly, and equipment to design innovative and modular, manufacturing cells in compliance with modern specifications. The result is the new flexible C-Frame Panel Assembly Cell (CPAC) Bulkhead riveting System. This paper describes how benchmarks for flexible automated drilling and fastening are being achieved with the CPAC.
2017-09-19
Technical Paper
2017-01-2073
Rick Calawa, Gavin Smith
Abstract The decision to replace a successful automated production system at the heart of a high volume aircraft factory does not come easily. A point is reached when upgrades and retrofits are insufficient to meet increasing capacity demands and additional floor space is simply unavailable. The goals of this project were to increase production volume, reduce floor space usage, improve the build process, and smooth factory flow without disrupting today’s manufacturing. Two decades of lessons learned were leveraged along with advancements in the aircraft assembly industry, modern machine control technologies, and maturing safety standards to justify the risk and expense of a ground-up redesign. This paper will describe how an automated wing spar fastening system that has performed well for 20 years is analyzed and ultimately replaced without disturbing the high manufacturing rate of a single aisle commercial aircraft program.
2017-09-19
Technical Paper
2017-01-2085
Sergey Lupuleac, Nadezhda Zaitseva, Margarita Petukhova, Julia Shinder, Sergey Berezin, Valeriia Khashba, Elodie Bonhomme
Abstract The paper is devoted to the simulation of A320 wing assembly on the base of numerical experiments carried out with the help of ASRP software. The main goal is to find fasteners’ configuration with minimal number of fastening elements that provides closing of admissible initial gaps. However, for considered junction type initial gap field is not known a priori though it should be provided as input data for computations. In order to resolve this problem the methodology of random initial gap generation based on available results of gap measurements is developed along with algorithms for optimization of fasteners' configuration on generated initial gaps. Presented paper illustrates how this methodology allows optimizing assembly process for A320 wing.
2017-09-19
Technical Paper
2017-01-2080
James Merluzzi, Isaac Bahr
Abstract Manually changing stringer-side tooling on an automatic fastening machine is time consuming and can be susceptible to human error. Stringer-side tools can also be physically difficult to manage because of their weight, negatively impacting the experience and safety of the machine operator. A solution to these problems has recently been developed by Electroimpact for use with its new Fuselage Skin Splice Fastening Machine. The Automatic Tool Changer makes use of a mechanically passive gripper system capable of securely holding and maneuvering twelve tools weighing 40 pounds each inside of a space-saving enclosure. The Automatic Tool Changer is mounted directly to the stringer side fastening head, meaning the machine is capable of changing tools relatively quickly while maintaining its position on the aircraft panel with no machine operator involvement.
2017-09-19
Technical Paper
2017-01-2075
Burton Bigoney, Nicholas Huddleston
Abstract Electroimpact and Lockheed Martin have developed an automated drilling and fastening system for C-130J aft fuselage panels. Numerous design and manufacturing challenges were addressed to incorporate the system into Lockheed Martin’s existing manufacturing paradigm and to adapt Electroimpact’s existing line of riveting machines for manufacture of these legacy aircraft parts. Challenges to automation included design of a very long yet sufficiently rigid and lightweight offset riveting anvil for fastening around deep circumferential frames, automated feeding of very short, “square” rivets in which the length is similar to the head diameter, creation of part programs and simulation models for legacy parts with no existing 3d manufacturing data, and crash protection for the aircraft part from machine collisions, given the uncertainties inherent in the model and the unique geometry of the aircraft parts.
2017-09-19
Technical Paper
2017-01-2082
Nirosh Jayaweera, Asitha Kulasekera, Posindu Maduranga, Thilina Kasun, Prabodh Seekkuarachchi, Janaka Sampath
Abstract Many components used in the aerospace industry are complex-shaped, without symmetric axes and parallel surfaces. Fabricating and repairing these components often require fixturing system to support manufacturing processes such as drilling, surface finishing, inspections and assembly. Currently available fixturing systems can be divided into dedicated and flexible fixtures. Among these, the flexible fixtures are suitable for rapidly changing fabricating processes and handling several complex-shaped components using same fixturing system. Background research suggested that the pin type fixturing system is the predominant design used in such applications to fix complex-shaped components. In pin type fixturing systems, force is applied to a single point of contact. This increases the pressure applied to the work piece and possibility of damaging these components. Further, conventional pins use rigid designs, which cannot adapt to the shape of the work piece.
2017-09-19
Technical Paper
2017-01-2094
Tyler Everhart
Abstract Electroimpact, in collaboration with Boeing, has developed an advanced robotic assembly cell, dubbed “The Quadbots.” Using Electroimpact’s patented Accurate Robot technology and multi-function end effector (MFEE), each robot can drill, countersink, inspect hole quality, apply sealant, and insert fasteners into the part. The cell consists of 4 identical machines simultaneously working on a single section of the Boeing 787 fuselage, two on the left, and two on the right. These machines employ “collision avoidance” a new feature in their software to help them work more synchronously. The collision avoidance software uses positional feedback from external safety rated encoders mounted to the motors on the robot. From this feedback, safe spaces, in the form of virtual boundaries can be created. Such that a robot will stop and wait if the adjacent robot is in, or going to move into its programmed work envelope.
Viewing 1 to 30 of 244

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